Honeywell KMH 880 User Manual Download

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SYSTEM INSTALLATION

MANUAL

KMH 880/KTA 870

MULTI-HAZARD AWARENESS

TRAFFIC ADVISORY SYSTEM

MANUAL NUMBER 006-10609-0003

REVISION 3 AUGUST, 2002

Summary of Contents for KMH 880

Page 1: ...SYSTEM INSTALLATION MANUAL KMH 880 KTA 870 MULTI HAZARD AWARENESS TRAFFIC ADVISORY SYSTEM MANUAL NUMBER 006 10609 0003 REVISION 3 AUGUST 2002 ...

Page 2: ...NAL INC Reproduction of this publication or any portion thereof by any means without the express written permission of Honeywell Interna tional Inc is prohibited For further information contact the Manager Technical Publications Honeywell International Inc ONE TECHNOLOGY CENTER 23500 West 105th Street Olathe KS 66061 Tele phone 913 782 0400 ...

Page 3: ...SYSTEM INSTALLATION MANUAL KMH 880 KTA 870 MULTI HAZARD AWARENESS TRAFFIC ADVISORY SYSTEM ...

Page 4: ...1 5 inch Binder 006 03140 0003 2 inch Binder 006 03140 0004 3 inch Binder 006 03140 0005 4 inch Post Binder WARNING Prior to Export of this Document review for export license requirement is needed COPYRIGHT NOTICE 2001 2002 Honeywell International Inc Reproduction of this publication or any portion thereof by any means without the express written permission of Honeywell International Inc is prohib...

Page 5: ...dividual publications PAGE ACTION Rev 0 Initial Release Insert Entire Manual Rev 1 B1 B2 Remove and Replace Appendix F Insert New Appendix Rev 2 Pages 2 17 and 18 Remove and Replace Pages 3 3 15 29 35 93 and 97 Remove and Replace Page 3 23 Figure 3 21 Add Section IV Remove and Replace Page D 11 12 Remove and Replace Rev 3 Pages 1 2 1 3 1 8 1 12 Addition of JTSO ref 1 1 Section 3 all drawings Repla...

Page 6: ...B KMH880 KTA 870 Rev 3 August 2002 10609I03 CDL Page R 2 THIS PAGE IS RESERVED ...

Page 7: ... Configuration Module 1 13 1 5 3 Antennas 1 13 1 6 INSTALLATION ACCESSORIES SUPPLIED 1 14 1 6 1 KMH 820 KTA 810 Installation Kit 1 14 1 6 2 Antenna Installation Kits 1 15 1 6 3 Databases 1 16 1 7 ACCESSORIES REQUIRED BUT NOT SUPPLIED 1 16 1 7 1 Temperature Probe 1 16 1 7 2 GPS Antenna Splitter 1 16 1 7 3 Miscellaneous 1 17 1 7 4 Cable And Wire 1 17 1 8 LICENSE REQUIREMENTS 1 17 1 9 INSTRUCTIONS FO...

Page 8: ...H 820 KTA 810 Processor Units 1 12 Table 1 11 KCM 805 Configuration Module 1 13 Table 1 12 KA 815 KA 92 Antennas 1 13 Table 1 13 GPS Cable Run Lengths 1 14 Table 1 14 KMH 820 KTA 810 Installation Kit 1 15 Table 1 15 KA 815 Installation Kit 1 15 Table 1 16 KA 92 Installation Kit 1 15 Table 1 17 Data Bases 1 16 Table 1 18 Temperature Probe 1 16 Table 1 19 GPS Antenna Splitter 1 17 Table 1 20 Miscell...

Page 9: ...rawing 2 21 Figure 2 5 KA 815 Doubler Plate Drawing 2 23 Figure 2 6 KA 92 Outline and Mounting Drawing 2 25 Figure 2 7 GPS Antenna Splitter 2 27 Figure 2 8 Coax Cable Treatment 2 30 Figure 2 9 Standard Coax Cable 2 30 Figure 2 10 Bulkhead In Line Connection Coax Cable 2 30 Figure 2 11 TNC Antenna Coax Connector Assembly 2 31 Figure 2 12 TNC Antenna Coax Connector Assembly 2 32 LIST OF TABLES Table...

Page 10: ...r Interface 3 33 Figure 3 5 KMH 820 KTA 810 Discrete Interface 3 35 Figure 3 6 KMH 820 KTA 810 Configuration Module Interconnect 3 37 Figure 3 7 KMH 820 KTA 810 Attitude Heading Interface 3 39 Figure 3 8 KMH 820 KTA 810 Radar Barometric Altitude Interface 3 41 Figure 3 9 KMH 820 KTA 810 Antenna Suppression Interface 3 49 Figure 3 10 KMH 820 KTA 810 EFS 40 50 Interface 3 51 Figure 3 11 KMH 820 KTA ...

Page 11: ...8 Configuration Tables 4 7 4 2 3 8 1 Category 1 Aircraft Mode Type Select 4 7 4 2 3 8 2 Category 2 Air Data Input Select 4 7 4 2 3 8 3 Category 3 Position Input Select 4 9 4 2 3 8 4 Category 4 Terrain Display Select 4 10 4 2 3 8 5 Category 5 Input Output Discrete Type Select 4 11 4 2 3 8 6 Category 6 Audio Menu Select 4 11 4 2 3 8 7 Category 7 Audio Output Level 4 11 4 2 3 8 8 Category 8 Altitude ...

Page 12: ...dio Menu Select 4 11 Table 4 8 Audio Output Level 4 12 Table 4 9 Altitude Monitor Option 4 12 Table 4 10 Terrain Display Alternate Pop Up Option 4 13 Table 4 11 Attitude and Heading Type 4 13 Table 4 12 Display Option Type 4 15 SECTION V CERTIFICATION 5 0 INTRODUCTION 5 1 5 1 CERTIFICATION PROCEDURE 5 1 5 1 1 Equipment Compatibility 5 1 5 1 2 Equipment Location 5 1 5 1 3 Federal Communication Comm...

Page 13: ... Rev 3 August 2002 10609I03 CDL TOC vii LIST OF APPENDICES APPENDIX A Mode C A 1 APPENDIX B STC B 1 APPENDIX C Certification C 1 APPENDIX D TASDiag D 1 APPENDIX E TSO E 1 APPENDIX F Airplane Flight Manual Supplement F 1 ...

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Page 15: ... 43 13 1B and AC 43 13 2A should be followed carefully to ensure a safe and electrically sound system installation The contents of this manual are for information and reference use only and must not be construed as a formal FAA approved work authorization It is highly recommended that prior to beginning the installation of the KMH 880 KTA 870 system that this manual is carefully reviewed Upon revi...

Page 16: ...coupled to the sys tem s simplicity practicality small size and weight with a minimum number of required aircraft sensors provides a formidable safety value NOTE The EGPWS portion of the KMH 820 is not suitable for helicopter operation No Radio Altimeter Landing Gear or Flap Discretes or Glideslope Receiver are necessary This significantly lowers the installation costs The KMH 880 is a system desi...

Page 17: ...urveilled aircraft and relative bearing of intruder aircraft with maximum installed accuracy of 30 with high reliability If the intruder aircraft is transponder equipped within ten nautical miles 10 000 feet relative altitude and TAS is not in interference limiting it will be reliably detected and reported 3 Timely data that does not lag more than 2 seconds behind the actual rela tive position as ...

Page 18: ... King KMH 820 Multi Hazard Awareness Processor 066 01175 0101 066 01175 2101 Directional Antenna Bendix King KA 815 TAS Directional Antenna 071 01599 0100 GPS Antenna Bendix King KA 92 GPS Antenna 071 01553 0200 Configuration Module Bendix King KCM 805 Configuration Module 071 00112 0100 Control Panel Display Bendix King KMD 540 Multi function Display 066 04035 0X01 Bendix King KAC 502 EGPWS Card ...

Page 19: ...SO C8c 066 01171 XXXX Bendix King IN 182A EGPWS Display 066 03084 003X TSO C63b Other displays that are compatible with ARINC 735A may be used to display traffic with this system The EGPWS data may also be displayed on Bendix King and AlliedSignal weather radar display units To put traffic on these weather radar dis plays the following adapter unit is required Bendix King GC 362A Graphics computer...

Page 20: ... EGPWS Modes of Operation a Optional Alerting and Warning Parameters The EGPWS may also be installed in aircraft that do not require FAA approved TAWS Systems and may be utilized with an optional set of alert ing and warning parameters that are designed especially for smaller piston aircraft and their normal flight characteristics ...

Page 21: ...a in the satellites navigation messages to solve for latitude longitude altitude horizontal velocity vertical velocity and current UTC GPS Data can also be supplied via the ARINC 743 743A and RS 232 KLN 94 interfaces A GPS Antenna Splitter could be used in liew of installing another antenna B TAS System 1 TAS Modes of Operation a Setup Mode The system shall be configured using an external PC via t...

Page 22: ...der represents a threat The TAS Processor shall also select proximate traffic and other traffic intruders to be displayed on the basis of their altitude relative to own aircraft The other traffic intruders are those that do not qualify to be TA or proximate traffic but are displayed NOTE Optional The TAS Processor may be controlled using discrete inputs C Options 1 Display Option TSO C151a Class B...

Page 23: ...arometric altimeter errors both in sensitive altime ters encoders and blind encoders Aircraft normally operated in very cold cli mates can benefit from the addition of an OAT probe interfaced to the EGPWS If the aircraft is equipped with an Air Data Computer which outputs Digital data with Corrected Altitude on an ARINC 429 port this can be used instead of an encoder and external OAT Probe OAT is ...

Page 24: ...0 03361 0000 Voltage Nominal 28 Vdc Range 22 to 30 Vdc Current Nominal 1 3 0 2 A Max Operating 1 65 0 2 A Bootup 3 3 0 5 A Power 46 2 3 Watts KTA 810 TRAFFIC ADVISORY UNIT P N 066 01152 0101 TSO COMPLIANCE PHYSICAL DIMENSIONS WEIGHT Installation Kit POWER REQUIREMENTS See Appendix E See Figure 2 1 See Figure 2 1 050 03361 0000 Voltage Nominal 28 Vdc Range 22 to 30 Vdc Current Nominal 1 15 0 2 A Ma...

Page 25: ...echnical Specifications KA 815 TRAFFIC ANTENNA P N 071 01599 0100 TSO COMPLIANCE PHYSICAL DIMENSIONS WEIGHT Installation Kit MOUNTING POWER REQUIREMENTS MAXIMUM AIRSPEED See Appendix E See Figure 2 3 0 95 lbs 050 03622 0000 See Figure 2 4 and 2 5 None 335 3 Knots Equivalent Air Speed EAS 600 Knots True Air Speed TAS and 55 000 feet Not To Be Exceeded NTBE 55 000 ft 600 knots Side slip for all the ...

Page 26: ...ermine whether that intruder repre sents a threat KA 92 GPS ANTENNA P N 071 01553 0200 TSO COMPLIANCE PHYSICAL DIMENSIONS WEIGHT Installation Kit MOUNTING POWER REQUIREMENTS See Appendix E See Figure 2 6 0 27 lbs 050 03318 0000 See Figure 2 6 5v supplied by the GPS receiver Table 1 9 KA 92 GPS Antenna Technical Specifications SYSTEM COMPONENT MANUFACTURER MODEL DESIGNER DESCRIPTION PART NUMBER TSO...

Page 27: ...essor will also be capable of supporting a top directional and bottom monopole antenna configuration In the latter configuration only intruders being tracked via the top directional antenna will have bearing infor mation The antennas will be vertically polarized and cover 360 degrees in azimuth and at least 10 to 20 degrees in elevation SYSTEM COMPONENT MANUFACTURER MODEL DESIGNER DESCRIPTION PART...

Page 28: ...00051 0060 Up to 46 ft These cables use R G 142 400 style connectors Note When using Non KPN or Non standard P N cables connectors etc the installer has the responsibility of proving airworthiness Table 1 13 GPS Cable Run Lengths SYMBOL PART NUMBER DESCRIPTION UOM 0000 010 00068 0026 TERMINALS CRIMP EA 8 J1 J3 J5 J7 J9 030 00134 0000 CONNECTOR COAX TNC EA 7 J4 J8 030 00480 0001 CONNECTOR RF PLG BN...

Page 29: ...R EA 1 M85049 38 25N STRAIN RELIEF FOR 128 PIN I O CONNECTOR EA 1 SYMBOL PART NUMBER DESCRIPTION UOM 0000 155 06059 0000 KA 815 Installation Drawing REF X M39012 30 0101 Connector TNC Rt Angle EA 4 MS24693 C54 Screw FHP 100 deg 8 32x1 00 EA 4 MS29513 148 O Ring EA 1 Table 1 15 KA 815 Installation Kit P N 050 03362 0000 SYMBOL PART NUMBER DESCRIPTION UOM 0000 030 00134 0001 Connector TNC Rt Angle E...

Page 30: ...re a Temperature Probe input if a Digital Air Data Computer with an OAT Label present on the bus is available as an interface 1 7 2 GPS Antenna Splitter To have the flexibility of using an existing KA 92 GPS Antenna Honeywell offers a splitter that will greatly simplify the installation procedure One of the split ports is DC blocked from the common port so that equipment voltage regulators do not ...

Page 31: ...y System SYMBOL PART NUMBER DESCRIPTION UOM QTY 050 03610 0003 GPS Antenna Splitter Kit EA 1 030 00134 0000 TNC Connector Straight EA 3 030 00134 0001 TNC Connector Rt Angle EA 1 Table 1 19 GPS Antenna Splitter P N 071 01600 0001 SYMBOL PART NUMBER DESCRIPTION UOM QTY 050 03610 0000 Basic Annunciator Kit EA 1 050 03610 0001 Terrain Radar Switching Kit EA 1 Table 1 20 Miscellaneous Accessories SYMB...

Page 32: ...ith the same type and voltage rating as originally installed If a relay malfunctions replace it with an air worthy relay having the same part number If a combination annunciator relay unit is used e g MD41 1208 1308 remove the unit and have it repaired by a factory rated service center If the aircraft is to fly with a relay or annunciator removed secure the connector s as necessary and placard the...

Page 33: ...es During ON condition or regularly scheduled maintenance inspect the wires and coax cables following the guidelines listed in AC 43 13 1B Chapter 11 as neces sary 1 9 7 Terrain Data Base Updates To order database updates contact Honeywell International Inc Navigation Ser vices Honeywell International Inc Aerospace Electronic Systems One Technology Center 23500 West 105th Street Olathe Kansas 6606...

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Page 35: ...oes not specifically identify acceptable conditions for the instal lation of the article The TSO applicant is responsible for documenting all limitations and conditions suitable for installation of the article An applicant requesting approval for installation of the article within a specific type or class of product is responsible for determining environmental and func tional compatibility 2 1 UNP...

Page 36: ... KTA 870 System installation will conform to standards designated by the customer installing agency and existing conditions as to the unit location and type of installation However the following suggestions should be carefully considered before installing your system 2 2 2 Avionics Cooling Requirements The most important contribution to improved reliability of all avionics equipment is to limit th...

Page 37: ...possible the KMH 820 KTA 810 should NOT be located in close proximity to equipment which produce considerable heat Locations which require disassembly of the aircraft to gain access are less desir able Any location that is exposed to moisture and or temperature extremes should be avoided Select a mounting location that allows sufficient clearance at the front of the unit for connectors and cables ...

Page 38: ...e CompactFlash card The terrain database card is removed and installed with power NOT applied to the system The KMH 820 may be removed from the aircraft to extract and install database cards if the mounting location does not provide enough clearance Updating the Terrain DataBase is accomplished by Moving the aluminum cover over the CompactFlash card out of the way Pressing the flash card ejector b...

Page 39: ...uxiliary audio input on the aircraft s audio control panel The audio output power level is set by programming the configuration mod ule 2 2 3 3 Installation Procedure A Slide the unit into the rack and secure it B Attach the harness to the front mating connector of the unit C Attach coax cables J1 thru J10 to the front of the unit Refer to Figure 2 1 and notes ...

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Page 41: ...B KMH 880 KTA 870 Rev 3 August 2002 10609I03 CDL Page 2 7 Figure 2 1 KMH 820 KTA 810 Installation Drawing Dwg No 155 06060 0000 Rev D Sheet 1 of 2 ...

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Page 43: ...B KMH 880 KTA 870 Rev 3 August 2002 10609I03 CDL Page 2 9 Figure 2 1 KMH 820 KTA 810 Installation Drawing Dwg No 155 06060 0000 Rev D Sheet 2 of 2 ...

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Page 45: ...it is installed in a location where the ambient tem peratures are 67 F to 158 F 55 C to 70 C 2 2 4 2 Installation Considerations A The Configuration Module must be mounted to the airframe within maxi mum cable harness length of 2 feet Make sure to leave adequate space to mount the Configuration Module when installing the Processor Unit 2 2 4 3 Installation Procedure A Install the Configuration Mod...

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Page 47: ...B KMH 880 KTA 870 Rev 3 August 2002 10609I03 CDL Page 2 13 Figure 2 2 Configuration Module Installation Drawing Dwg No 155 06061 0000 Rev A ...

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Page 49: ...plate for the antenna installations NOTE The L band omni directional has not been tested for the direct effects of lightning and the installer TC or STC applicant must determine the suit ability of the antenna for the specific installation NOTE KMH 880 KTA 870 Systems REQUIRE that the antenna installation guidelines be followed Adherence to these guidelines will assure that crit ical specification...

Page 50: ...e aircraft skin which is horizontal during enroute flight Antenna baseplate must be level within or 5 in longitudinal and lateral axes when the aircraft is in level flight Refer to Figures 2 4 and 2 5 and notes C The antenna must be mounted on a nearly flat surface such that the antenna contacts the bare metal skin all around the perimeter without gaps when normal mounting screw torque is applied ...

Page 51: ...B KMH 880 KTA 870 Rev 3 August 2002 10609I03 CDL Page 2 17 Figure 2 3 KA 815 Antenna Outline Drawing ...

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Page 53: ...hould also be observed Refer to Figure 2 6 and notes B Mount the GPS antenna on the aircraft skin which is horizontal during enroute flight Antenna baseplate must be level within or 5 in the longi tudinal and lateral axes when the aircraft is in level flight 2 2 6 2 Installation Procedure A Make sure the antenna is well bonded to the aircraft skin B Make sure the antenna is sealed to the aircraft ...

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Page 55: ...B KMH 880 KTA 870 Rev 3 August 2002 10609I03 CDL Page 2 21 Figure 2 4 KA 815 Installation and Mounting Drawing Dwg No 155 06059 0000 Rev B ...

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Page 57: ...B KMH 880 KTA 870 Rev 3 August 2002 10609I03 CDL Page 2 23 Figure 2 5 KA 815 Doubler Plate ...

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Page 59: ...B KMH 880 KTA 870 Rev 3 August 2002 10609I03 CDL Page 2 25 Figure 2 6 KA 92 Outline and Mounting Drawing Dwg No 155 06019 0000 Rev 2 ...

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Page 61: ...B KMH 880 KTA 870 Rev 3 August 2002 10609I03 CDL Page 2 27 Figure 2 7 GPS Antenna Splitter Dwg No 071 01600 0001 ...

Page 62: ... Connectors are also defined All lengths are defined as end to end Any in line or bulkhead penetrations must be evaluated separately It is the installing agency s responsibility to show airworthiness of the fabricated cable assemblies When determining cable type and length make the following assumptions A Attenuation of each straight TNC male connector is 0 06 dB 1 03 GHz using a 030 00134 0000 RF...

Page 63: ...mi nation of loss 3 The maximum allowable signal loss between the KA 91 92 antenna and the KMH 820 cannot exceed 8 0 dB Refer to the following table to determine the loss between the antenna and the KMH 820 Table 2 1 Signal Loss Part Number Description Signal Loss per Item Example Quantity Example Signal Loss Actual Quantity Actual Signal Loss 071 01600 0001 GPS Antenna Splitter 3 4 dB 1 ea 3 4 dB...

Page 64: ...B KMH 880 KTA 870 Rev 3 August 2002 10609I03 CDL Page 2 30 Figure 2 8 Coax Cable Treatment Figure 2 9 Standard RG 400 Coax Cable Figure 2 10 Bulkhead In Line Connection RG 400 Coax Cable ...

Page 65: ...B KMH 880 KTA 870 Rev 3 August 2002 10609I03 CDL Page 2 31 Figure 2 11 TNC Antenna Coax Connector Assembly ...

Page 66: ...B KMH 880 KTA 870 Rev 3 August 2002 10609I03 CDL Page 2 32 Figure 2 12 TNC Antenna Coax Connector Assembly ...

Page 67: ... CST Monday through Friday 3 0 1 Applicable Part Numbers Sub section Description Information given in this section pertains only to the KMH 880 KTA 870 System using part numbers Refer to Section 1 4 1 for complete part number descriptions 3 0 2 Function Sub section Description Detailed information concerning the purpose and operation of the interface are described in this section 3 0 3 Requirement...

Page 68: ... shields as shown in the interconnect diagrams cause unacceptable interference due to noise sources on the aircraft double shielded wire may be substituted for single shielded wire shown in this manual The outer shield must be grounded at both ends to comply with HIRF and Lightning require ments The inner shield may then be grounded at a single end to protect against the aircraft noise source Norm...

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Page 71: ... 1 65 0 2 Amps 28 VDC Max operating 3 3 Amps 18 VDC maximum current Power 46 2 3 Watts B DC Return J10 127 128 These pins connect to airframe ground with 22 gauge wire minimum NOTE The KMH 820 KTA 810 will shut down when the power line dips below 15 VDC The KMH 820 KTA 810 will resume normal operation i e surveilling targets on power restoration when the power line meets 18 VDC mini mum 3 1 2 On D...

Page 72: ... 36 VDC ON GROUND 10 ohms or 0 to 3 5 VDC J10 4 Air_Gnd NOTE The normal mechanical failure mode will be the airborne condition 3 1 4 Landing Gear Discrete Input The Landing Gear Discrete if used will present a standard open circuit when the gear is retracted and a standard ground when the gear is extended RETRACTED 100Kohms to airframe DC GND or 18 5 to 36 VDC EXTENDED 10 ohms to airframe DC GND o...

Page 73: ...rocessor will cause annunciations to be inhibited when higher priority events occur i e wind shear alerts terrain alert warnings NOTE The TAS Computer Unit will inhibit certain functions which would tend to distract the pilot when faced with a potentially hazardous condition such as windshear or terrain alerts These conditions are presumed to have a more immediate possibility and higher probabilit...

Page 74: ...his output will remain in the activated state for the duration of the advisory unless cancelled or inhibited ACTIVE GROUND 10 ohms to ground VOLTAGE 0 to 3 5 VDC INACTIVE OPEN Current Capability 200 milliamps when activated Voltage Capability 36 VDC when not activated J10 24 VIS_ANNUN_TRAFFIC 3 1 10 Synthesized Voice output KMH 820 KTA 810 will supply low level audio signals of up to 100 milliwatt...

Page 75: ...mperature operations J10 109 OAT_H J10 110 OAT_L J10 111 OAT_Ref 3 1 12 GPS Input GPS information is furnished in ARINC 429 and RS 232 NEMA or RNAV formats The following Information is required from the GPS 1 Latitude Longitude 2 Ground Speed 3 True Track Angle 4 GPS Altitude 5 Indication of the quality of the navigation solution VFOM and HFOM prefered Optional information to be used if available ...

Page 76: ...s The TAS Processor BITE function is responsible for executing the test outlined below during cold start or functional test to ensure that the TAS Processor and inputs from interfacing components are functional 1 Automatic System Performance Monitoring SPM and Functional Test The TAS Processor SPM and functional test functions will test the TAS Pro cessor for correct operation detection of interna...

Page 77: ... activate the normal TAS display functions D Cancel any TA voice message If a fault is detected that would invoke one of the above responses then that response will be accomplished within one second of detecting the fault 3 Failure Categories A Catastrophic The severity of a catastrophic failure will preclude any software from exe cuting B Fatal The severity of a fatal failure will preclude any TA...

Page 78: ...where available This resolution is not needed for flat areas J10 126 GND_DISC_15 Terrain Awareness Inhibit 3 1 14 Terrain Warning This is a means of displaying to the flight crew that there is a critical situation involving terrain clearance and corrective action is required J10 116 TERRAIN WARNING 3 1 15 Terrain Caution This is a means of displaying to the flight crew that there is a terrain clea...

Page 79: ... systems This discrete is internally wired to the TAS advisory inhibit and is available on J10 22 ADV_INHIBIT 3 1 18 EGPWS Terrain Inop and Terrain not available Output The EGPWS produces one monitor output This discrete reflects the EGPWS Inop and Terrain Inop Terrain Not Available functions This discrete activates with the loss of EGPWS power The status of this discrete is also contained on an A...

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Page 95: ...H 880 KTA 870 Rev 3 August 2002 10609I03 CDL Page 3 29 Figure 3 3 KMH 820 KTA 810 System Interconnect Block Diagram KMH 920 KTA 910 System Interconnect Block Diagram Dwg No 155 01735 0002 Rev C Sheet 1 of 2 ...

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Page 97: ...H 880 KTA 870 Rev 3 August 2002 10609I03 CDL Page 3 31 Figure 3 3 KMH 820 KTA 810 System Interconnect Block Diagram KMH 920 KTA 910 System Interconnect Block Diagram Dwg No 155 01735 0002 Rev C Sheet 2 of 2 ...

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Page 99: ...B KMH 880 KTA 870 Rev 3 August 2002 10609I03 CDL Page 3 33 Figure 3 4 KMH 820 KTA 810 Power Interface KMH 920 KTA 910 Power Interface Dwg No 155 01735 0003 Rev A ...

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Page 101: ...B KMH 880 KTA 870 Rev 3 August 2002 10609I03 CDL Page 3 35 Figure 3 5 KMH 820 KTA 810 Discrete Interface KMH 920 KTA 910 Discrete Interface Dwg No 155 01735 0004 Rev B ...

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Page 103: ...B KMH 880 KTA 870 Rev 3 August 2002 10609I03 CDL Page 3 37 Figure 3 6 KMH 820 KTA 810 Configuration Module Interconnect KMH 920 KTA 910 Configuration Module Interconnect Dwg No 155 01735 0005 Rev A ...

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Page 105: ...B KMH 880 KTA 870 Rev 3 August 2002 10609I03 CDL Page 3 39 Figure 3 7 KMH 820 KTA 810 Attitude Heading Interface KMH 920 KTA 910 Attitude Heading Interface Dwg No 155 01735 0006 Rev A ...

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Page 107: ...880 KTA 870 Rev 3 August 2002 10609I03 CDL Page 3 41 Figure 3 8 KMH 820 KTA 810 Radar Barometric Altitude Interface KMH 920 KTA 910 Radar Barometric Altitude Interface Dwg No 155 01735 0007 Rev A Sheet 1 of 4 ...

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Page 109: ...880 KTA 870 Rev 3 August 2002 10609I03 CDL Page 3 43 Figure 3 8 KMH 820 KTA 810 Radar Barometric Altitude Interface KMH 920 KTA 910 Radar Barometric Altitude Interface Dwg No 155 01735 0007 Rev A Sheet 2 of 4 ...

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Page 111: ...880 KTA 870 Rev 3 August 2002 10609I03 CDL Page 3 45 Figure 3 8 KMH 820 KTA 810 Radar Barometric Altitude Interface KMH 920 KTA 910 Radar Barometric Altitude Interface Dwg No 155 01735 0007 Rev A Sheet 3 of 4 ...

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Page 113: ...880 KTA 870 Rev 3 August 2002 10609I03 CDL Page 3 47 Figure 3 8 KMH 820 KTA 810 Radar Barometric Altitude Interface KMH 920 KTA 910 Radar Barometric Altitude Interface Dwg No 155 01735 0007 Rev A Sheet 4 of 4 ...

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Page 165: ...ignal multipath are not a factor The bearing accuracy tests should be conducted outside away from operating aircraft 115 VAC 60 Hz power may be required for the test equipment CAUTION ADVISE THE LOCAL AIR TRAFFIC CONTROL BEFORE TESTING THE TRANSPONDERS OR THE KMH 880 KTA 870 SYSTEM WITH A SYNTHETIC ALTITUDE TO ACKNOWLEDGE POSSIBLE INTERACTION WITH OTHER TAS TCAS EQUIPPED AIRCRAFT 4 2 CONFIGURATION...

Page 166: ...WS Installed and Operating B Interconnect Cable C IBM or Compatible PC D A Copy of Honeywell WINVIEWS NOTE WinViews is an Enhanced GPWS diagnostic communications program that runs from Windows on a PC that is connected to the EGPWS WinViews HELP as well as many other menu items are active even though the program is fully oper ational when communications are established with the EGPWS 4 2 3 2 Confi...

Page 167: ... number of categories and the remaining numbers before the second separator reflect the ID for each of the categories String breakdown Explanations CUW The command to write 0 String Version Separator 11 the number of categories 0 Category 1 ID 0 TSO C151a Class B curve set 1 Category 2 ID 1 Altitude Encoder with 500 ohm Temperature Probe 0 Category 3 ID 0 GPS Internal GPS Express RS 232 0 Category...

Page 168: ...eters Pin Assignment Signal Mnemonic RS 232TXD_MON J10 99 RS 232RXD_MON J10 100 4 2 3 5 Configuration Sequence of Events Application A Turn the KMH 880 system power on B Bring up the WINVIEWS program Type Ctrl Z C At the WINVIEWS prompt type CFG Press the ENTER key D Type in the pre configured STRING using the command CUW Press the ENTER key E After loading this string in the WINVIEWS the cursor w...

Page 169: ...s the procedure to determine the Config uration ID selection required for any given aircraft installation STEP CATEGORY SIGNAL SELECTION INSTRUCTION IDENT NO 1 Selects a Aircraft Type b Mode Type Using Table 4 2 and any sub tables contained within locate the Aircraft Mode type Record the Ident ID No on the space available on Ident column of this table _____ ID 2 Selects a Air Data Source Using Tab...

Page 170: ...tude Monitor Disable Using Table 4 9 and any sub tables contained within select the desired True or False Condition for Altitude Monitor Display Disable Altitude Monitor Callout Disable and Alti tude Monitor Disable Record the Ident ID No on the space available on Ident column of this table _____ ID 9 Selects a TA D alternate Pop Up Using Table 4 10 and any sub tables contained within select the d...

Page 171: ...ypes and asso cated parameters In this category only the following parameters are to be defined Basic mode alert and warning thresholds Table 4 2 Aircraft Mode Type Select NOTE When selecting ID 0 Category 6 Audio Menu Select must select ID 1 Alter nate in order to be in compliance with TSO C151a 4 2 3 8 2 Category 2 Air Data Input Select The following table provides identification of the Air Data...

Page 172: ...te and SAT 003 003 8 5 None RS 232 422 Air Data Computer Shadin 200 003 003 9 5 T3 RS 232 422 Air Data Computer Shadin 200 with SAT 003 003 10 6 None RS 232 Encoded Altitude Shadin Digitizers for UPS Appollo at 1200 bps 003 003 11 6 T1 RS 232 Encoded Altitude Shadin Digitizers for UPS Appollo at 1200 bps with 500Ω OAT Temperature Probe 003 003 12 7 None RS 232 Encoded Altitude Shadin 17 Byte at 96...

Page 173: ... Table 4 4 Position Input Select ID AIR DATA TYPE STATIC AIR TEMPERA TURE TYPE DESCRIPTION EFFECTIVITY App Cfg 19 11 T1 RS 232 Encoded Altitude Magellan at 1200 bps with 500Ω OAT Temperature Probe 003 003 20 11 None RS 232 Encoded Altitude ARNAV at 9600 bps 003 003 21 11 T1 RS 232 Encoded Altitude ARNAV at 9600 bps with 500Ω OAT Temperature Probe 003 003 ID POSITION INPUT TYPE DESCRIPTION GPS ALTI...

Page 174: ...ontrol and the output 429 bus The TA D Pop Up Disable function is defined by a Boolean See Table 4 10 In this category the following signals are configured by the ID number Table 4 5 Terrain Display Select SIGNAL NAME SIGNAL TYPE DEFINED BY Terrain Display Bus ASPB or ARINC Display configuration Group Range Bus ARINC 429 Display Input Control Group TA D Alternate Pop Up Boolean Defined directly in...

Page 175: ...ry 1 selected ID 0 TSO C151a Class B curve set Category 6 ID 1 Alternate must be selected to be in compliance with the TSO 4 2 3 8 7 Category 7 Audio Output Level The following provides identification of the Audio Output Level type Each entry in the ID column corresponds to a particular nominal alert output level selec tion max 6dB 12 dB 18dB AND 24Db The Nominal Max Output is 100 mW rms for the 6...

Page 176: ...e 4 9 Altitude Monitor Options ID VOLUME TYPE EFFECTIVITY App Cfg 0 Max 600 ohm ª 100mW 001 001 1 6 dB 001 001 2 12dB 001 001 3 18dB 001 001 4 24dB 001 001 ID GEOALT DISPLAY LABEL TEXT ALTITUDE MONITOR DISABLE ALTITUDE MONITOR CALLOUT DISABLE ALTITUDE MONITOR DISPLAY DISABLE EFFECTIVITY App Cfg 0 MSL False False False 003 003 1 MSL False False True 003 003 2 MSL False True False 003 003 3 MSL Fals...

Page 177: ... Table 4 10 Terrain Display Alternate Pop Up Option 4 2 3 8 10 Category 10 Attitude and Heading Select The following Table provides identification of the Attitude and Heading type Each entry in the Attitude and Heading column has a corresponding Table that provides detailed information on the configuration ID TA D ALTERNATE POP UP DISABLE EFFECTIVITY App Cfg 0 False 001 001 1 True 001 001 ID ATTIT...

Page 178: ...llows the selection of how the terrain display operates at slower speeds The various speeds selectable below allow terrain display operation to meet varying operator demands This Category selects the output type orientation and function of the EGPWS s terrain display More specifically this selection will determine the operation of the terrain display output when on the ground Upon start up and whe...

Page 179: ...Effectivity App Cfg 0 0 Classic Fixed Wing 45kts valid 15kts invalid North up 003 003 1 1 Blank w message 003 003 2 2 No limit 1kts valid i e always valid North up 003 003 3 3 Blank w message 003 003 4 4 10kts 15kts valid 5kts invalid North up 003 003 5 5 Blank w message 003 003 6 6 15kts 20kts valid 10kts invalid North up 003 003 7 7 Blank w message 003 003 8 8 20kts 25kts valid 15kts invalid Nor...

Page 180: ... the TAS C Attitude Type Not Installed or ARINC 429 Data ARINC 429 magnetic heading BCD or Binary pitch angle and roll are input to the TAS Processor via the Attitude Magnetic Heading ARINC 429 high speed input bus D Radio Altimeter Type Not Installed ARINC 429 Bendix King Analog Sperry Analog Collins Analog or ARINC 552A The Radio Altimeter Source Port will input to the TAS Processor The input im...

Page 181: ... ARINC 429 that interfaces to the TAS Processor G Controller Type ARINC 735 Protocol or Discrete Control The Controller Type will determine the type of control data either the Control Panel to the TAS Processor via the CNTL HD RX ARINC 429 input bus or via Discrete Control switches H Ground Headphone Volume 1 25 2 5 5 10 20 40 80 100 mw The on ground headphone level will be configurable to the abo...

Page 182: ...ive This should be set to disable for aircraft installations 4 2 4 1 TAS RS 232 Maintenance Port One port is provided which meets the characteristics specified in RS232C This bus can be used to access internal data from the TAS for aircraft testing In addition to the internal data other items such as unit configuration and flight history can also be accessed Baud Rate 38 400 Parity none Data Bits ...

Page 183: ...nal 4 3 2 EGPWS Ground Test Procedures 066 01175 x101 only This Ground Test Procedure is designed to minimize potential equipment dam age and verify proper operation of the Honeywell EGPWS as installed in the air craft A Review your aircraft installation drawings against the manufacturer s data sheets and verify that all necessary connections are included on your drawings and that the pin numbers ...

Page 184: ...Now look at the PC screen and locate the item named Gill ham Alt ft and verify that the altitude shown agrees with the aircraft altime ter 100 feet If it does not troubleshoot the encoding altimeter wiring L Provide a source of GPS signals to the GPS antenna This can be accom plished by using a GPS repeater inside a hanger or by taking the aircraft outside where it has a clear view of the sky M Pr...

Page 185: ...fy that the PC dis play shows the item named Gillham Alt ft at 1000 feet 100 feet S Set up the pitot static test set to allow an ascent to 30 000 feet or to the maximum altitude of the lowest rated device attached to the static system If for example the aircraft uses a blind encoder rated to 25 000 feet the altitude to climb to would be 25 000 feet You must verify that all equipment connected to t...

Page 186: ...The Post installation test is used to apply power and functionally check out the system Successful completion of the post installation test verifies the proper operation of the KMH KTA Traffic Advisory Sys tem A To check the aircraft system interconnections perform the following Check that all cables and interwiring are installed according to the Interwir ing and Cable Fabrication instructions par...

Page 187: ...28Vdc and 26Vac 400 Hz power sources are operational i e check power bus meter Check that the aircraft 5Vac or Vdc or 28 Vdc panel background lighting power source and dimmer control is operational by adjusting the cockpit dimmer switch for proper cockpit panel background illumination Check that the Transponder TAS and Radar Systems are OFF If applica ble the selected encoding altitude source shou...

Page 188: ...rol Panel The following events should occur during the test period On the traffic display a test pattern will be displayed that allows verification of each type of intruder symbol that can be displayed During the self test the word TEST is displayed on the display The following symbols are dis played Traffic Advisory yellow circle will appear at 9 o clock range of 2 miles 200 feet below and climbi...

Page 189: ...l _____ Pull the 1 amp TAS Control circuit breaker Verify that the TAS flag appears on the traffic display Reset the circuit breaker verify that the flag clears Pass Fail _____ NOTE The following three steps should only be performed when the configuration mod ule is set to use the Display Valid input Pull the Traffic Display circuit breaker NOTE The above circuit breaker should be for the unit pro...

Page 190: ...ail _____ Test the ABOVE NORMAL BELOW function as follows On the TAS Control Panel set the ABOVE NORMAL BELOW to ABOVE On the traffic display screen ABOVE should be annunciated Traffic between 2700 feet below and 8700 feet above can be displayed Select BELOW The screen should annunciate BELOW in place of the ABOVE annunciation Traffic between 8700 feet below and 2700 feet above can be displayed Se...

Page 191: ...nd 7 nautical mile range rings ______ Set TAS RANGE switch to 10 nautical miles The following properly scaled range rings should be visible 2 and 10 nautical mile range rings ______ Set TAS RANGE switch to 15 nautical miles The following properly scaled range rings should be visible 2 and 15 nautical mile range rings ______ Set TAS RANGE switch to 20 nautical miles The following properly scaled ra...

Page 192: ...parate Man Auto switch open MAN_AUTO CP 66B J1 pin 23 and verify that TAS information is displayed on the Multi Functional Display only when TAS has been selected on it regardless of whether there is a TA in effect Pass Fail _____ 3 If applicable check that the traffic modes T WX can be selected on the color radar indicator as follows Set the T WX switch to indicate WX Weather Only Observe that th...

Page 193: ...h 0 0 _________ The Heading Status on the computer should indicate VALID The heading type should indicate Synchro or ARINC 429 Flag the heading source by pulling the circuit breaker Verify that the Heading Status goes INVALID Verify that the TAS flag appears on the traffic display Reset the circuit breaker Verify that the TAS flag clears Pass Fail ______ 5 Verify that the encoding altitude is prop...

Page 194: ..._____ feet Altitude at 19 000 feet the computer screen indicates ______ feet Transponder indicates ______ feet Altitude at 31 800 feet the computer screen indicates ______ feet Transponder indicates ______ feet NOTE The above test step checks both logic states for all Gillham lines Other tests may be adequate for some installations Flag the encoding altitude source by pulling the circuit breaker V...

Page 195: ...cuit breaker Verify that the Pitch and Roll Status goes INVALID Verify that the TAS flag appears on the traffic display Reset the circuit breaker Verify that the TAS flag clears Pass Fail ______ 6 If applicable verify that the Radio Altimeter is properly interfaced to the TAS Processor Confirm the radio altitude configuration straps and measure the input at the KMH KTA Processor The TAS and radio ...

Page 196: ...t 2 500 feet the Diagnostic Computer indicates ______ feet Flag the Rad Altitude source by pulling the circuit breaker Verify that the Rad Alt Status goes INVALID Verify that the TAS flag appears on the traffic display Reset the circuit breaker Verify that the TAS flag clears Rad Altitude Source 1 Pass Fail ______ 7 Check that the configuration module and logic discretes are correct Refer to suppo...

Page 197: ...etween 00 H and 93 H Do all items Pass Fail ______ 8 Perform the Ramp test This test requires the use of a TCAS Ramp Tester Specific instructions for operating the ramp tester are contained in the applicable operator s manual Using the TCAS Ramp Tester exercise the TAS with the various intruder aircraft scenarios Monitor the displays and aural messages to verify that system response is correct Eva...

Page 198: ...ning at 10 NM at an altitude of 50 500 feet at a closure rate of 450 KTS and an altitude rate of 0 FPM An alternate scenario may be required for some test sets Initiate the intruder test on the TCAS Ramp Tester Verify that the intruder symbol corresponds to the scenario in bearing distance and relative altitude Confirm that the audio announcement agrees with the scenario The intruder symbol will b...

Page 199: ...er operation of the flight level mode on the traffic displays Traffic Display ______ 9 If installed verify that the GPWS and Windshear warnings and TAS voice alerts are compatible Also verify that the GPWS and Windshear warnings have been prioritized over the TAS voice alerts Another test to check the Advisory Inhibit Inputs can be performed with the Diagnostic Computer Initiate the TAS self test ...

Page 200: ... Antenna must have unob struted line of sight to each other NOTE The landing gear logic must simulate RETRACTED UP whenever checking the bearing accuracy to the bottom antenna TAs will appear as No Bearing targets when the gear position logic is EXTENDED DOWN because the bot tom antenna is in omni directional mode To insure proper antenna selection the relative altitude difference between the simu...

Page 201: ...00 feet or greater Disable the WOW logic to put the aircraft systems in the AIRBORNE mode Set up the TCAS Ramp Tester on headings listed in the following figure On each heading in a CW direction initiate an intruder test scenario on the TCAS Ramp Tester and measure the relative bearing to the intruder from the traffic display Whenever testing the bottom directional antenna set the landing gear log...

Page 202: ...nal procedure is used during installation of the TAS system to automatically align the top and bottom TAS antennas to the aircraft To begin the Bore Sight procedure start by setting up the ramp tester as described in Section 4 3 3 paragraph E 8 Using the IFR 201 Ramp Test Set create a scenario to simulate a Mode C transponder equipped aircraft at 2NM at an altitude of 50 000 feet and an altitude r...

Page 203: ...uccessful one of the following errors will be reported A Bore Sight Failed Cable calibration failed Cable calibration occurs automatically during normal operation If the unit is unable to complete the cable calibration then a bore sight calibration will not be performed Check cable connections from TAS to the antenna Check TAS fault LED to verify that there are no fatal failures and retry the proc...

Page 204: ...ta 2 offsets for the selected antenna will be stored in the configuration module TAS will automatically shut down and restart after the procedure has been completed to begin using the new antenna offsets After the Bore Sight Procedure has successfully completed The Bearing Accuracy Test E 10 should be re run at 30 0 and 30 to confirm that the bore sight procedure has improved bearing accuracy 12 P...

Page 205: ...B KMH 880 KTA 870 Rev 3 August 2002 10609I03 CDL Page 3 99 Figure 3 22 KMH 820 KTA 810 Processor Front Connector ...

Page 206: ...B KMH 880 KTA 870 Rev 3 August 2002 10609I03 CDL Page 3 100 Figure 3 23 KMH 820 KTA 810 Front Connector Cable ...

Page 207: ...B KMH 880 KTA 870 Rev 3 August 2002 10609I03 CDL Page 3 101 Figure 3 24 KMH 820 KTA 810 Rear Connector Cable ...

Page 208: ...ALT_C4 BOTH I 16 GIL_ALT_C2 BOTH I 17 GIL_ALT_C1 BOTH I 18 GIL_ALT_D4 TAS I 19 GIL_ALT_D2 TAS O 20 PH_HI TAS HEADPHONE O 21 PH_LO TAS HEADPHONE I 22 ADV_INHIBIT BOTH MUTE GND I 23 TAS_STANDBY TAS STBY GND O 24 VIS_ANNUN_TRAFFIC TAS TRAFFIC GND O 25 TAS_VALID TAS VALID GND O 26 SPARE_DO1 TAS X O 27 SPARE_DO2 TAS X I 28 HEADING_VALID TAS I 29 HEADING_H TAS I 30 HEADING_C TAS I 31 HEADING_X TAS I 32 ...

Page 209: ..._RS232_TERMRDY TAS X I O 68 SUPPRESSION TAS 18V ACTIVE I 69 CNTL_RX_A TAS I 70 CNTL_RX_B TAS I 71 ABV_BEL_NORM TAS Above Below Norm I 72 CONFIG_MOD_DATA_IN TAS O 73 CONFIG_MOD_DATA_OUT TAS O 74 CONFIG_MOD_CHIP_SEL TAS O 75 CM_CLOCK TAS O 76 CM_ 5V TAS O 77 CM_GND BOTH I 78 SPARE_RX_A TAS X I 79 SPARE_RX_B TAS X O 80 SPARE_TX_A TAS X O 81 SPARE_TX_B TAS X I 82 AIRCRAFT POWER PS O 83 EGPWS RETURN EG...

Page 210: ...I 110 OAT_L EGPWS AIR TEMP O 111 OAT_REF EGPWS AIR TEMP REF 112 n c X I 113 GSE_PRES BOTH FACTORY TEST O 114 ADC_TXB EGPWS I 115 ADC_RXB EGPWS O 116 DISC_OUT_01 EGPWS LAMP ALERT O 117 DISC_OUT_02 EGPWS WARNING ALERT O 118 DISC_OUT_03 EGPWS WX SELECT I 119 HEADING VALID LO TAS HEADING VALID LO O 120 MON_OUT_1 EGPWS EGPWS INOP I 121 GND_DISC_07 EGPWS SELF TEST I 122 GND_DISC_08 BOTH X I 123 GND_DISC...

Page 211: ...business hours are 8 00 AM to 5 00 PM Central Time Monday through Friday The TAS system may operate in conjunction with and in close proximity to a transponder The functions of the system will not in any way degrade the perfor mance of the transponder beyond its specified limits All of the TAS requirements stated in this document will be met when the TAS equipment is operating in conjunction with ...

Page 212: ...ng FAA Form 337 or whether a Supplemental Type Certifi cate STC will be required If FAA Form 337 is determined to be sufficient the installing agency should determine the acceptability of the procedures defined within this manual If the FAA Inspector determines that an STC is required the installing agency will need to contact the nearest Aircraft Certification Office ACO to obtain acceptable proc...

Page 213: ... sample is to be used as a guide to acceptable content and format and not intended to apply to all installations It is the responsibility of the installing agency to prepare an appropriate Flight Manual Supplement and obtain FAA approval 5 1 8 Pilot Briefing The installing agency should carefully review the Flight Manual Supplement and the KMH 880 KTA 870 System Operator s Manual P N 006 18265 000...

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Page 215: ...e 6 1 SECTION VI OPERATION 6 0 INTRODUCTION Refer to Section IV of this manual for the operating instructions for the post installation checkout Refer to the KMH 880 KTA 870 System Operator s Manual P N 006 18265 0001 for complete operating instructions ...

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Page 217: ...B KMH 880 KTA 870 Rev 3 August 2002 10609I03 CDL Page A 1 APPENDIX A Mode C Surveillance Range ...

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Page 221: ...B KMH 880 KTA 870 Rev 3 August 2002 10609I03 CDL Page B 1 APPENDIX B STC Appendix ...

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Page 225: ...B KMH 880 KTA 870 Rev 3 August 2002 10609I03 CDL Page C 1 APPENDIX C CERTIFICATION APPENDIX SAMPLE CERTIFICATION CHECKLIST ...

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Page 227: ...ecifications of TSO C147 Class A and TSO C151a Class B B Ground and flight tests were conducted and determined that the KMH 880 KTA 870 System does not interfere with normal operation of other equipment installed in the aircraft and the KMH 880 KTA 870 System equipment is not a source of objection able electromagnetic interference Proper operation and accuracy were verified and the unit functions ...

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Page 229: ...B KMH 880 KTA 870 Rev 3 August 2002 10609I03 CDL D 1 APPENDIX D DIAGNOSTIC APPENDIX ...

Page 230: ...RNING DO NOT USE THE TASDIAG PROCESSOR FIELD DIAGNOSTIC PRO GRAM WHILE AIRBORNE THE PROGRAM IS USED ONLY WHILE THE AIRCRAFT IS ON THE GROUND THE SYSTEM IS DEGRADED TO PERFORM MAINTENANCE FUNCTIONS AND IS NOT AIRWORTHY WHILE RUNNING THE DIAGNOSTIC SOFTWARE NOTE The diagnostic tests are performed with KMH 880 KTA 870 installed in the aircraft ...

Page 231: ...og Data D 9 7 Configuration Module Options D 10 7 1 View Strap Data D 11 7 2 Modify Strap Data D 11 7 3 Save to Text File D 12 7 4 Save to Binary File D 13 7 5 Copy from Binary File D 13 7 6 Initialize Config Module D 14 7 7 Bore Sight Top Bottom Antenna D 14 8 Intruder Data D 15 8 1 Overwrite View D 16 8 2 Capture View D 17 9 Viewing Cable Calibration Data D 17 10 Viewing Current System Status D ...

Page 232: ...w Continuous Window D 8 Figure 3 Diagnostic and Log Data Window D 10 Figure 4 View Strap data Window D 11 Figure 5 Modify Straps Window D 12 Figure 6 Copy Binary File Window D 14 Figure 7 Intruder Data Window D 15 Figure 8 Cable Calibration Data Window D 18 Figure 9 System Status Window D 19 Figure 10 TAS S W Window D 20 ...

Page 233: ... written to a user specified file by clicking Save from the File menu The active selected window will be saved A TAS Diag demonstration mode in which no RS 232 communications are present is available for familiarizing the user with the program Select Demo Mode from the File menu This document is an operations manual for TAS Diag providing tips and techniques enabling TAS Diag to be a useful tool i...

Page 234: ...ntinuously attempt to establish communica tions until communication is established or the Cancel button is pressed Once com munications are established and the TAS unit has completed initialization TAS Diag will accept user input NOTE If the TAS unit is powered on but communications are not being established ensure that the computer s COM port is connected to the TAS unit s RS 232 diagnostics port...

Page 235: ...tions for the TAS Diag program WARNING TAS DIAG IS NOT INTENDED FOR USE DURING FLIGHT TAS DIAG IS AN INVASIVE PROGRAM AND MAY INTERFERE WITH TIMING INTERVALS OF THE TAS PROCESSOR THIS MAY CAUSE INTERMITTENT TAS FAILURES POWER MUST BE CYCLED ON THE TAS PROCESSOR AFTER TAS DIAG HAS BEEN CONNECTED AND BEFORE ANY FLIGHTS OCCUR ...

Page 236: ...miliarizing the user with available options The demonstration mode does not require an RS 232 connection to a TAS unit Any option may be selected and a simulation TAS unit response will occur 5 Inspecting Current Processor I O Data There are two options for inspecting the TAS unit s I O data single snapshot or con tinuous see Figure 2 Figure 2 I O Data View Continuous Window ...

Page 237: ...ot repeated every one to two seconds The TAS unit sends the data to the I O Continuous Window A slight screen flicker will be noticeable as each new screen of data is written The red Stop button on the button bar will be enabled as long as communications are on going and the window is being updated To stop the update click the Stop button 6 Inspecting TAS Unit s Internal Diagnostic and Log Data On...

Page 238: ...t power cycle are not in the Diagnostic and Log Data since the Log is written at the end of each power cycle 7 Configuration Module Options The user will be offered options to view the strap data modify the strap data save to a text file save to a binary file copy from a binary file and initialize the configuration module ...

Page 239: ...ap Data Window NOTE For new installations of Equipment or the Configuration Module use the Initialize Config Mod option see Appendix D Section 7 6 7 2 Modify Strap Data The strap data is read from the TAS unit and displayed in a dialog box see Figure 5 The dialog box has two pages Strap Page 1 and Strap Page 2 Click on the top of each page to view modify the different straps The user may modify an...

Page 240: ... be prompted as to whether or not to write the data to the configuration module Click the cancel button to exit without saving changes If the user opts to write the data to the configuration module a message window will appear informing the user that the data is being written the TAS unit is resetting and the user should wait until the initialization is complete When the TAS unit is ini tialized a...

Page 241: ...Copy from Binary File This option allows the user to program the configuration module with data previ ously stored in a binary file When this option is selected a window allowing access to all binary file names in the current PC directory is displayed see Figure 6 When a file is clicked the description entered when it was saved is displayed in the File Description Field When a file is selected by ...

Page 242: ...a to verify modify the configura tion The user may click the Cancel button at any time to end the initialization pro cess without actually writing to the configuration module When the Strap configuration is complete click the OK button to save it to the con figuration module 7 7 Bore Sight Top Bottom Antenna This option is used during initial installation of the TAS system to auto matically align ...

Page 243: ...ons Complete is displayed in the pop up message box Click OK to close the message box If an error is reported refer to Section 4 of this manual for troubleshooting techniques When the Bore Sight procedure is successfully completed the Delta 1 and Delta 2 offsets for the selected antenna will be stored in the configuration module TAS will automati cally shut down and restart after the test has been...

Page 244: ...dicates that the intruder is non altitude reporting NAR Ant This is an indication of the antenna on which the intruder is being surveilled A T indicates the top antenna while a B indicates the bottom antenna power The measure power of the last received from the intruder A power of 255 indicates no reply was received from the intruder A power of zero indicates that a power and or bearing could not ...

Page 245: ...dically by the TAS unit so that bearings may be computed as accurately as possible This option allows the user to view the results of the most recent cable calibration and causes the cable calibrations to be performed at an accelerated rate Cable calibrations are normally spaced at 3 minute intervals but this option causes the spacing between the end of one cable calibration and the start of the n...

Page 246: ...ewing Current System Status This option allows the user to view the current TAS unit system status without hav ing to try to read the LEDs located on the side or front of the TAS unit see Figure 9 This data may be viewed two different ways Overwrite or Continuously The status is updated every second or two The system s status is indicated along with the state of the LED indicator When a fault occu...

Page 247: ... is erased before each update For the overwrite mode click Overwrite View on the Sys Status Menu For continuously click Con tinuous View on the Sys Status Menu Figure 9 System Status Window 11 TAS S W Info This option allows the user to retrieve TAS unit specific software see Figure 10 ...

Page 248: ...o a IFR 201B ramp tester can be used to reply to the TAS unit To turn this option on or off click Ramp Tester Mode on the File Menu When the option is on a check mark appears to the left of Ramp Tester Mode on the File Menu Selecting this mode will set own aircraft altitude to 50 000 feet The traffic display will display TEST rather than TA Only when in this mode ...

Page 249: ... can not establish communications with the TAS unit the first thing to check is the Comm port to which the RS 232 is connected The RS 232 setting on the File Properties dialog box should not be changed However the Comm serial port needs to be selected for the port connected to the TAS unit Usually Comm 1 is the correct port If you have several ports you may have to experiment by chang ing the Comm...

Page 250: ...B KMH 880 KTA 870 Rev 3 August 2002 10609I03 CDL D 22 THIS PAGE IS RESERVED ...

Page 251: ...ingout of spec F 01 13 PowerSupply 250Vvoltagedivider onIObdreadingout of spec F 01 14 PowerSupply 2 5Vreference F 01 15 CPUinstructionerror F 01 16 Transmit power readonIObdisreadingout of spec IOBITE FAULTS F 02 01 TopAntenna matchingresistoronIObdnot correct or 50Ωloadsnot connected F 02 02 BottomAntenna matchingresistoronIObdnot correct or 50Ωloadsnot connected F 02 03 BaroAltimeter 419 429 co...

Page 252: ... error External control bit on video bd F 04 15 Video MD3X Mode C error MD3X bit on video bd BITE DURATION FAULTS F 10 XX SW task duration error XX is MultiTask task number BITE FREQUENCY FAULTS F 20 XX SW task frequency error XX is MultiTask task number BITE EXCEPTIONS F 81 00 ITE Task In Progress BITE test not completed before arting again software error F 81 01 BITE SW Monitor Invalid MT task n...

Page 253: ...W_EXCEPT should never get software error F 85 04 OS_DMA_1030_SW_EXCEPT 1030 Receive DMA buffer size exceeded DMA on computer bd or software error that we should never get F 85 05 Config Mod CRC F 85 06 Config Mod Compatibility Code F 85 07 Config Mod Data Comparison can get only when writing F 85 50 IO_VOICE_MBOX_EXCEPTION MT mailbox system not working software error F 85 51 IO_DR_MBOX_EXCEPTION M...

Page 254: ... 89 04 MODEC_SUPPRESSION_EXCEPTION suppression not set during interrogation F 89 05 MODEC_EOI_STUCK_EXCEPTION EOI should transition at end of interrogation on video bd F 89 06 DMA_COUNT1_EXCEPTION too many replies or DMA error F 89 07 DMA_COUNT2_EXCEPTION too many replies or DMA error F 89 08 VILIMIT_DEFAULT_EXCEPTION should never get software error F 89 09 VCCAL_INIT_EXCEPTION unable to get a val...

Page 255: ...B KMH 880 KTA 870 Rev 3 August 2002 10609I03 CDL E 1 APPENDIX E TSO APPENDIX ENVIRONMENTAL QUALIFICATION FORMS ...

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